Helicopter equipped with a device for emergency lift assistance

Abstract

The invention relates to a helicopter including a structural framework, at least one main rotor for lift and propulsion integral with said structural framework and a drive train for driving said main rotor including a power transmission gearbox and at least one main engine, wherein it further includes a plurality of extra booster power units fixed to said structural framework and configured so as to be able to supply extra lift of the helicopter in case of failure of the helicopter's drive train.

The invention claimed is: 
     
       1. A helicopter comprising
 a structural framework, 
 at least one main rotor for lift and propulsion integral with said structural framework and 
 a drive train for driving said main rotor comprising 
 a power transmission gearbox and at least one main engine, further comprising 
 a plurality of extra booster power units fixed to said structural framework and configured so as to be able to supply extra lift of the helicopter in case of failure of the helicopter's drive train, wherein each of said extra booster power unit is mounted detachably on the structural framework and wherein the structural framework further comprises 
 upper frames arranged in the vicinity of the main rotor for lift and propulsion, and in that said extra booster power units are fixed on said upper frames. 
 
     
     
       2. The helicopter according to  claim 1 
 wherein each of said extra booster power unit is mounted detachably on the structural framework by detachable fixing means. 
 
     
     
       3. The helicopter according to  claim 1 , wherein the helicopter comprises four extra booster power units uniformly distributed on said structural framework. 
     
     
       4. The helicopter according to  claim 1 , wherein said extra booster power units comprise pyrotechnic devices. 
     
     
       5. The helicopter according to  claim 1 , wherein the helicopter comprises a control unit connected to each of said extra booster power units and configured for controlling the activation of each of said extra booster power units in case of a failure in the helicopter's drive train. 
     
     
       6. The helicopter according to  claim 5 , wherein said control unit is configured so as to be able to activate the extra booster power units automatically as the ground is approached. 
     
     
       7. The helicopter according to  claim 1 , wherein said extra booster power units are configured so that each one is able to supply identical propulsive power and in that said extra booster power units are arranged and oriented on said structural framework in such a way that said extra booster power units exert thrust forces in directions intersecting at a single point, called the convergence point (C). 
     
     
       8. The helicopter according to  claim 7 , wherein said convergence point (C) is arranged at the centre of the rotor in the plane of the rotor blades, in such a way that the resultant of the thrust forces of the extra booster power units is vertical and is applied at the top of a rotor mast. 
     
     
       9. The helicopter according to  claim 7 , wherein said convergence point (C) is the centre of gravity of the helicopter.